Abstract: The present work is part of a comprehensive heat transfer and filmcooling study on a locally cooled nonaxisymmetric contoured turbine endwall. A new test rig consisting of a linear cascade of three prismatic vanes at unity ...

Abstract: Internal coolant passages of gas turbine vanes and blades have various orientations relative to the external hot gas flow. As a consequence, the inflow of film cooling holes varies as well. To further identify the influencing ...

Abstract: The current study investigates the flow conditions of a twin scroll asymmetric turbine. This is motivated by the operating conditions of the turbine at a heavyduty reciprocating internal combustion engine with exhaust gas ...

Abstract: An experimental and numerical study of the flow field and the downstream film cooling performance of cylindrical and diffuser shaped cooling holes is presented. The measurements were conducted on a flat plate with a single ...